Parametric study of wind tunnel test section configurations for stabilizing normal shock wave structure

Shock Waves ◽  
2019 ◽  
Vol 30 (1) ◽  
pp. 77-90 ◽  
Author(s):  
P. M. Ligrani ◽  
S. M. Marko
Keyword(s):  
Shock Wave ◽  
Wind Tunnel ◽  
Parametric Study ◽  
Test Section ◽  
Wind Tunnel Test ◽  
Wave Structure ◽  
Normal Shock ◽  
Shock Wave Structure ◽  
Normal Shock Wave

Newtonian hypersonic theory for normal shock wave structure.

AIAA Journal ◽  
1968 ◽  
Vol 6 (1) ◽  
pp. 170-171 ◽  
Author(s):  
WILLIAM B. BUSH ◽  
ROBERT ROSEN
Keyword(s):  
Shock Wave ◽  
Wave Structure ◽  
Normal Shock ◽  
Shock Wave Structure ◽  
Normal Shock Wave

scholarly journals A Steam Ejector Refrigeration System Powered by Engine Combustion Waste Heat: Part 2. Understanding the Nature of the Shock Wave Structure

2019 ◽  
Vol 9 (20) ◽  
pp. 4435 ◽  
Author(s):  
Yu Han ◽  
Xiaodong Wang ◽  
Lixin Guo ◽  
Anthony Chun Yin Yuen ◽  
Hengrui Liu ◽  
...  
Keyword(s):  
Shock Wave ◽  
Waste Heat ◽  
Wave Structure ◽  
Back Pressure ◽  
Normal Shock ◽  
Engine Fuel ◽  
Refrigeration System ◽  
Shock Wave Structure ◽  
Steam Ejector ◽  
Shock Region

In general, engine fuel combustion generates 30% waste heat, which is disposed to the environment. The use of the steam ejector refrigeration to recycle the waste heat and transfer them to useful energy source could be an environmentally friendly solution to such an issue. The steam ejector is the main component of the ejector refrigeration system, which can operate at a low-temperature range. In this article, the internal shock wave structure of the ejector is comprehensively studied through the computation fluid dynamics (CFD) approach. The shock wave structure can be subdivided into two regions: firstly the pseudo-shock region consisting of shock train and co-velocity region; secondly the oblique-shock region composed of a single normal shock and a series of oblique shocks. The effect of the shock wave structure on both pumping performance and the critical back pressure were investigated. Numerical predictions indicated that the entrainment ratio is enhanced under two conditions including (i) a longer pseudo-shock region and (ii) when the normal shock wave occurs near the outlet. Furthermore, the system is stabilized as the back pressure and its disturbance is reduced. A critical range of the primary fluid pressure is investigated such that the pumping is effectively optimized.

Numerical Investigation of a Normal Shock Wave Boundary Layer Interaction in a 4.3 Aspect Ratio Test Section

2016 ◽  
Author(s):  
Miranda P. Pizzella ◽  
Sally Warning ◽  
Mary Jennerjohn ◽  
Mark W. McQuilling ◽  
Ashley Purkey ◽  
...  
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Aspect Ratio ◽  
Numerical Investigation ◽  
Test Section ◽  
Normal Shock ◽  
Ratio Test ◽  
Normal Shock Wave ◽  
Boundary Layer Interaction ◽  
Wave Boundary

Sonic Flow Through an Abrupt Change in Cross-Section

1984 ◽  
Vol 198 (3) ◽  
pp. 197-203 ◽  
Author(s):  
J S Anderson ◽  
G E A Meier
Keyword(s):  
Shock Wave ◽  
Abrupt Change ◽  
Wave Structure ◽  
Normal Shock ◽  
Laser Doppler Velocimeter ◽  
Normal Shock Wave ◽  
One Dimensional ◽  
Sonic Flow ◽  
Flow Through ◽  
The One

The steady, transonic flow in a rectangular duct following an abrupt change in section has been studied by measuring the density with a Mach-Zehnder interferometer and velocity with a laser-Doppler velocimeter. The flow structure was controlled either by a single, normal shock wave or by a series of reflected oblique shocks. In the case of the normal shock wave structure the one-dimensional compressible flow theory was found to apply adequately to the overall duct. Within the duct the flow was not one-dimensional, but had a minimum velocity in the centre and four shear layers.

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